Dirigible device



Jan. 12 1926. I

J. H. HAMMOND, JR

DIRIGIBLE DEVICE Ogigixial F iled June 11,1915 7 Sheets-Sheet 1 INVENTORJan. 12 1926.

J. H. HAMMOND, JR

DIRIGIBLE DEVICE 7 Sheets-Sheet 2 o igi al Filed June 11,1915

A'H'ORNEY bwm Jan. 12 1926.

J. H. HAMMOND, .JR

DIRIGIBLE DEVICE Original Filed ne 11,1915

'7 Sheets-Sheet 3 INVENTOR Hi 12 ATTORNEY Jan. 12 1926.

J. H. HAMMOAND, JR

DIRIGIBLE DEVICE Original Filed June 11,1915

7 Sheets-Sheet 4 INVENTOR ATTORNEY z omm \mm c Jan. 12 1926. 1,568,974

, J. H. HAMMOND, JR

DIRIGIBLE DEVICE Original Filed June 11,1915 '7 sheets-sheet s INVENTORz w W ATTORNEY Jam 12 {1926. 1,568,974

- J. H. HAMMOND, JR

DIRIGIBLE DEVICE ()riginal ile une 11,1915 7 Sheets-Sheet a INVENTOR 7 Wmow M 8 6 I R .w mm D ME mm I H m m H. D l 6 2 1 2 1 Jan.

riginal Filed June 11,1915 7 Sheets-Sheet 7 sion of my Patented Jan. 12,1926.

UNITED STATES PATENT OFFICE.

DIRIGIBLE DEVICE.

Original application filed June 11, 1915, Serial No. 33,450. Divided andthis application filed November have invented certain new and usefulIm-' provements in Dirigible Devices, of which the following is aspecification.

Primarily one of the objects of this invention is to provide an improvedair craft which when in operation may be automatically maintainednormally upon a predetermined course, but which may be controlled ordirected selectively from a distance through the agency of wireless orradiant energy. This application is a diviapplication Serial No. 33,450,filed June 11,- 1915, for improvements in dirigible devices.

In the accompanying drawings, which show but one of the many possibleembodiments of this invention;

Figs. 1 and 2 are diagrammatic fragmentary views (Fig. 1 being partiallyin 1S0- metric), which taken together, disclose an I aeroplaneconstructed in accordance with this invention;

Fig. 3 is an enlarged side elevation partly in vertical section of aportion of the same looking in the direction of the arrow 33 on Fig. 1;

Figure 4 is an enlarged end elevation of a portion of the same lookingin the direction of the arrow 4-4 on Fig. 1;

Figure 5 is a fragmentary side elevation of a pneumatic device embodyinga part of this invention;

Fig. 6 is a top plan View of the device shown in Fig. 5;

Fig. 7 is a side elevation of a detail of the device shown in Figs. 5and 6;

Fig. 8 is an enlarged longitudinal section of a reciprocatory valveembodying a part of this invention;

Fig. 9 is an enlarged vertical central section of a pneumatic clutch andmeans cooperating therewith, embodying apart of this invention Figs.10,11 and 12 are enlarged longitudinal sectional views of a rotary valveem bodying a part of this invention, the valve being shown in threesuccessive operative positions in the three views respectively;

Figs. 13 to 21 are transverse sections on Serial No. 677,450.

lines 13-13 to 2121 'of Fig. 10 respectively.

Referring to the drawings, one embodiment of this invention comprises anaeroplane, more specifically a'biplane includin as usual two mainsubstantially parallel planes 30 and 31 fixed to the body or frame 32 ofthe aeroplane and extending transversely thereof, and any suitablepropelling apparatus (not shown) for driving the aeroplane through theair.

For steering the aeroplane laterally or rotating the aeroplane about anormally substantially vertical axis, a vertical rudder 35 is pivotallymounted upon a vertical post 36 depending downwardly from and rigid withthe rear end of the body 32 of the aeroplane, the rudder 35 beingarranged to oscillate about an axis 3737 fixed with respect to theaeroplane and normally extending substantially vertically.

For steering the aeroplane vertically or rotating the aeroplane about atransverse normally substantially horizontal axis a horizontal rudder 38is pivotally mounted upon the rear end of the body 32 of the aeroplaneto oscillate with respect thereto about an axis 39'-39 fixed withrespect thereto and extending transversely thereof and normallysubstantially horizontally.

For tilting, or rotating, or for balancing the aeroplane about thelongitudinal axis of the aeroplane, any well known or suitable means maybe provided, but in the form shown two ailerons or auxiliary planes 40,41, are pivotally secured to the opposite ends of the main planes 30, 31and are arranged to oscillate simultaneously in opposite directions withrespect thereto about alined axes 4242 and 4343 extending substanframeor body of the aeroplane and arranged to be energized by any suitablemeans (not shown) and to automatically control the vertical rudder 35.

The gyroscopic stabilizer or controller 50 is of a well known formcomprising four rotary elements or gyroscopes 60, 61, 62 and 63 whichare suitably mounted within and supported by two concentric rings 65 and66, the inner one of which, 65, is mounted to oscillate upon horizontaldiametrically opposed pivots 67 and 68 extending transversely of theaeroplane and carried by the outer ring 66, and the outer ring 66 ismounted upon two diametrically opposed pivots 69 and 70 rigid therewithand extending longitudinally of the aeroplane and at right angles to thetransverse pivots 67 and 68. The longitudinal pivots 69 and 70 aremounted in bearings 71 and 72 respectively,

to swing about an axis fixed with respect to the aeroplane and extendinglongitudinal thereof. Depending downwardly and centrally from the innerring, 65 and rigid therewith is an arm 75 which is maintained in avertical position in a well known manner by the action of the gyroscopes60, 61, 62 and 63. Mounted upon the lower end of the arm 75 to rotatewith respect thereto about a vertical axis fixed with respect-to the armis a roller which engages loosely and rotatably in a substantiallysemicircular groove 81 provided therefor in a substantially semicircularrocker 82 to the ends of which are rigidly secured two opposed alinedpivots 83 and 84 which are rotatably supported in spaced bearings 85 and86 fixed upon the body of the aeroplane, whereby the rocker 82 ismounted to swing about an axis coincident with the axes of the pivots 83and 84 and extending transversely of the body of the aeroplane and fixedwith respect thereto.

The axis of oscillation of the rocker 82 is also always in a verticalplane which includes the axes of the transverse pivots 67 and 68.

For automatically controlling the horizontal rudder electrically asaresult of the action of the gyroscopic stabilizer 50, a segmentalcontact support 90 is rigidly secured to the transverse ivot 83 and isprovided with two insulated alined segmental electric contacts 91 and 92rigidly secured thereto and the adjacent ends of which are slightlyseparated by a rectangular piece of intermediate insulation 93 which isalways maintained by the hereinbefore described gyroscopic means in aposition above the transverse pivot 83 and in a vertical plane includingtheaxis of the transverse pivot 83. C0- operating separately with thesegmental contacts 91 and 92 is a transverse reference con,- tact '94which is rigid with and insulated from a radial arm 95 projectingupwardly from and rigid with a transverse pivot 96 mediate insulation101;

which is mounted in a support 97 rigid with the body of the aeroplane tobe adjustable about an axis coincident with the longitudinal axis of thetransverse pivot 83 supporting the rocker 82 for a purpose that will beset forth hereinafter. The reference contact 94 is arranged to slidablyengage either of the segmental contacts 91 or 92 or to rest out ofcontact with either upon the intermediate insulation 93.

For automatically controlling the ailerons 40 and 41 electrically as aresult of the action of the gyroscopic stabilizer, the longitudinalpivot 69 of the stabilizer has fixedly secured thereon a segmentalcontact support 98 provided with two insulated alined segmental electriccontacts 99 and 100 rigidly secured thereto andslightly spaced from eachother by a rectangular piece of inter- Arranged to cooperate separatelywith the two segmental contacts 99, 100 is a' reference contact 102which is rigid with a radial arm 103 rigid with a pivot 104 mounted torotate in a support 105 fixed upon the body of the aeroplane, thereference contact being thus arranged to oscillate about an axiscoincident with the axis of the longitudinal pivot 69. The intermediateinsulation 101 is .always maintained by the gyrosocopic stabilizer in aposition above and in a vertical plane including the axis of thelongitudinal pivot 69; and the reference contact 102 is arranged toslidably engage either of the segmental contacts 99, 100 or to rest outof contact with either upon the intermediate insulation 101.

For supplying power to oscillate the horizontal rudder 38 and theailerons 40, 41, there are two parallel spindles and 111 which extendlongitudinally of the aero plane and which are arranged to be ro- -tatedeither in one direction or in the opposite direction and eitherseparately or together about axes fixed with respect to the aeroplane.Rigidly secured to these two spindles respectively are two pulleys 112and 113. Around the pulley 112 is wound a flexible wire or rope.114which is carried over suitable idlers 115 and 116 and the ends of whichare secured respectively to the ends of a rod 117 perpendicular to andrigid with the horizontal rudder whereby when the pulley 112 is rotatedeither in one direction .or the other, the horizontal rudder 38 will beoscillated accordingly. The other pulley 113 is similarly connected by aflexible wire or rope 120 extending over idlers 121 and by branch wiresor ropes 122 extending over idlers 123, 123 and 124, 124 with the endsof two rods 125 and 126 perpendicular to and rigid with the I twoailerons 40,- 41 respectively in such a ailerons will be simultaneouslyoscillated accordingly in opposite directions so that when the free endof either aileron rotates upwardly, the free end of the otheraileronwill rotate downwardly.

For actuating or rotating the spindles 110 and 111 either in onedirection or in the opposite direction, a propeller 130 is rigidlysecured to one end of a shaft 131 extending longitudinally of theaeroplane and arranged to be' rotated by the propeller 130 about an axisfixed with respect to the aeroplane as the aeroplane moves through theair. Motion is transmitted from the rop'eller shaft 131 to the spindles110 and 111 through a pinion 132 rigidly secured to the propeller shaftand engaging two driving gears 133 and 134, coaxial respectively withthe spindles 110 and 111.v gears 133 and 134 are operatively connectedin a well known manner through internal gears (not shown) with tworeversing gears 135 and 136, the driving gears 133 and 134 being thusarranged to rotate continually in one direction and the reversing gears135 and 136 to rotate continually in an opposite direction. Motion istransmitted from either of the driving gears 133, 134 or from either ofthe reversing gears 135, 136

to the spindles 110 or 111 respectively by means of four magneticclutches including four solenoids 140, 141, 142 and 143, four clutchmembers 144, 145, 146 and 147 rigid ly connected to the four gears 133,135, 134 and 136 respectively and four clutch members 148, 149, 150 and151 independently movable into and out of clutching relationrespectively as a result of the energization and deenergizationv of thecorresponding solenoids 140, 141, 142 and 143.

For energizing the solenoids 140, 141, 142 and 143 either automatically,or selectively, as will appear hereinafter, to control the horizontalrudder 38 and the ailerons 40, 41, the outer ends of one pair ofsolenoids 140, 141 are connected by wires 155=and 156 with thecorresponding.segmental contacts 91 and 92, and their inner ends areconnected by wires 157 and 158 through a battery 159 with thecorresponding transverse reference contact 94; and the outer ends of theother pair of solenoids 142, 143 are connected by wires 160, 161 withthe corresponding segmental contacts 99, 100 and their inner ends areconnected by wires, 162, 163 through a battery 164 with thecorresponding longitudinal reference contact 102. i

For automatically oscillating the vertical rudder to control the lateralmovement of the aeroplane, the azimuth gyroscope or other suitableazimuth maintaining means is provided with an arm 175 which is at alltimes electrically insulated from the gyroscope but which is arranged tobe opera- The driving 7 .s pp

tively connected to the gyroscope or disconnected therefrom selectivelythrough the action of a pneumatic clutch as will appear hereinafter.During the automatic control of the vertical rudder during any givenperiod by the gyroscope, the arm 175 is operativel connected to thegyroscope through t e action of the pneumatic clutch and is maintainedby the gyroscope substantially in a vertical plane intersecting thehorizon at a given point throughout the period. Upon opposite sidesrespectively of the central position of the free end of the arm 175' andarranged to be engaged thereby, are two electrical contacts 176 and 177which are held against rotation about a vertical axis with respect tothe aeroplane. Opposed light spiral springs 178, 179 tend to hold thefree end of the arm 17 5 substantially midway between the contacts 17 6,177 whenthe arm is not under the control of the gyroscope, but thesesprings yield to permit of the control of the arm by the gyroscope. Thearm 17 5 cooperates with the contacts 176 and 17 7 to control thevertical rudder automatically as will appear hereinafter.

To permit of the selective control of the aeroplane by an operatorlocated at a distance, the aeroplane is provided with pneumatic means ordevices controlled'by means responsive to radiant energy for selectivitycontrolling the horizontal rudder 38 and the ailerons 40, 41 by suitablyvarying the positions of the reference contacts 94 and 102 of thegyroscopic stabilizer 50, and for disconnecting the azimuth gyroscopefrom its arm 175 and selectively controlling the vertical rudder 35, aswill appear. hereinafter.

The pneumatic means for selectively controlling the aeroplane includes asource of 199 of compressed air or other motive uid and a rotary valve200 arranged in a fixed valve casing 201 and connected to the source ofair supply 199 by a pipe 202 and branch ,pipe 203, as will appearhereinafter. For giving a step by step rotary movement to the valve200,which in the construction shown is a movement of degrees at each step,and in one direction only, the valve is provided at one end with a stem205 projecting outwardly through the easing 201, and a segmental gear206 is loosely mounted upon the stem and carries pivoted thereto aratchet 207 which engages a ratchet wheel208 fixed upon the stem 205.

An oscillatory movement is given to the sega spring 213. The cylinder211 is connected to the source of air supply 199-by a pipe 220 I toforce the "rack 209 outwardly the valve 200, through one step, 1n thiscase which communicates with the cylinder through suitable inlet ports214, 215 and passage 216, which leads from the cylinder and is alsoarranged to communicate with two exhaust ports 217, 218. The admissionof air from the pipe 220 into, and the exhaust of air from the spacewithin the cylinder back of the piston through the inlet and exhaustports is controlled by a reciprocatory piston valve 225 provided withfour annular recesses 225. This valve 225 is connected to and controlledby a core. 226 of a solenoid 227. The rack 209 is normally maintained inits innermost position with respect to the cylinder 211 by the spiralsprlng within the cylinder, and the solenoid 227 is normally deenergizedand the piston valve 225 is normally held in its innermost position by asuitable spring normally maintaining the inlet into the cylinder fromthe pipe 220 closed and the exhaust ports 217 and 218 open.

For energizing and deenergizing the solenoid 227 to control theaeroplane at the will of an operator at a distance, means responsive toradiant energy in the form of electromagnetic waves are providedincluding any suitable open oscillatory receiving circuit 235 associatedwith a suitable closed oscillatory circuit includin an inductance 236,condensers 237, 238, a v,etector 239 and a relay including anelectromagnet 240 having a Ipivoted armature 241 arranged to en age axed control 242 normally held out 0 engagement therewith by a spring243. One end of the solenoid 227 is connected to the armature 241 by awire 244 extending through a battery 245, and the other end of thesolenoid 227 is connected to the fixed I contact 242 bya'wire 246. Theconstruction is such that when an impulse ofradiant magnet 240 isenergized and closes the circuit through the battery-245 thus energizingthe soleno d 227 and drawing its core 226 inwardly to-open the inletinto the cylinder to rotate through 60- degrees. When the radiantimpulse ceases the armature 241, core 226 and rack 209 are returned totheir normal positions under the action of their respective springsleaving the rotary valve in the position into which it has been rotated.

For distributing compressed air from the source of supply 199'to.variousdevices for selectively controlling an aeroplane as will appearhereinafter, the rotary valve 200 is provided as shown in Figs. 10'to 21with a plurality of recesses and passages, including fivecircumferential or annular recesses 250, 251, 252, 253 and 254 which forclearness .may be named the outermost orfirst 250,

second 251, third 252, fourth 253 and fifth 254 respectively. These fiveannular recesses are, arranged to communicate at all times respectivelywith five transverse passages 255, 256, 257, 258 and 259 providedtherefor through the valve casing 201.

The rotary valve 200 is also provided with two pairs of diametricallyopposed longitudinal recesses 265, 266, 267, 268 leading inwardly fromthe outermost annular recess 250, and with a' pair of diametricallyopposedlongitudinal recesses 269, 270 leading outwardly from the secondannular recess a 251, these longitudinal passages 'being slightly longerin each case than half the distance between the first and and secondannular recesses 250, 251 and thus adapted to register or communicate inturn with a transverse passage 271 provided therefor through the valvecasing midway between vided therefor through the valve casing.

Also, two pairs of diametrically v-opposed longitudinal recesses 277,278, 279, 280 are spaced in the valve between the second and thirdannular recesses 251 and 2.52, the enter ends of these longitudinalrecesses being arranged to register or communicate successively with thefour transverse passages 273, 274, 275, 276, and the lower ends of thesefour longitudinal recesses 277 to 280 being arranged to register orcommunicate s cessivel with two pairs of diametrical y op ose passages281, 282, 283 and 284 pro vi ed therefor through the casing. Extend--ing beneath the surface of-the valve is a passage 285, one end of whichopens through the surface of the valve at a point midway between thelongitudinal recesses 278 and 279-and so located that the upper end ofthis passage will register or communicate successively with fourtransverse passages 273, 274, 275 and 276 through the valve casing.

The rotary valve 200 is also provided with a longitudinal recess 286extending inwardly from the fourth annular recess 253 and with fivespaced longitudinal recesses 287, 288, 289, 290, 291 extending outwardlyfrom the fifth annular recess 254 all of these longitudinal recessesbeing arranged to communitransverse reference contact 94, there ismounted upon the aeroplane a pneumatic device (see Fi 1, 5, 6 and 7)including a shaft 300 whic is arranged to rotate about an axis fixedwith respect to the aeroplane in bearings 301, 302. Rigidly secured tothe shaft 300 are twospaced ratchet wheels 303 and 304, the teeth of oneratchet wheel being arranged to face in a direction of rotation opposedto the direction of rotation faced by the teeth of the other ratchetwheel. Between the two ratchet wheels .303 and 304 and loosely mountedupon the shaft 300 is a gear wheel 305, which carries pivotallyconnected to the opposite sides thereof two oppositely extending pawls306 and 307 arranged to engage the two ratchet wheels 303 and 304respectively. Engaging the inner ends of the two pawls respectively aretwo springs 308, 309 which are fixed upon the opposite sides of the gearwheel 305 and Y which tend to press the inner ends of the pawls intoengagement with their ratchet wheels. Two diametrically opposed fixedsegmental cams or guides 310 and 311 are arranged upon opposite sides ofthe gear 305 and normally engage'the outer ends of both pawls to holdthe pawls out of engagement with the ratchet wheels, but these cams arearranged to permit either one of the pawls to be moved automaticallyinto engagement with its ratchet wheel while the other pawl is held outof engagement with its ratchet wheel, upon a suitable rotation of thegear wheel 305 through'a small arc. For rotating the gear 305 through asmall arc in either direction, the gear is provided along only a part ofits circumference with teeth 315 and these are engaged by a rack 316which is rigid with a piston rod 317 which extends through a fixed powercylinder 318 in which a suitable piston 319 is fixed upon the rod.

- For centralizing the piston rod 319 of the pneumatic device forselectively controlling the horizontal rudder, the piston rod.- 317 alsoextends through a spring cylinder 320 in which it is surrounded by aspiral spring 321 which is compressed between two discs 322, 323,arranged in the spring cylinder and loosely. surrounding the piston rod317 and pressed against the inner surfaces of the end walls of thespring cylinder. Normally engaging the outer surfaces of the two discsare two collars 324, 325 fixed upon the piston rod 317 and arranged toreciprocate therewith freely through apertures 326 and 327 provided terefor in the opposite ends of the spring cylinder.

For'reciprocating the piston 319 to control the horizontal rudder theopposite ends of the cylinder 318 are connected by pipes 330 and 331 tothe transverse passages 274 and 276 of the casing of the rotary valve200 so that when the valve 200 is in a given less rope or wire 336 whichalso extends over suitable idlers 337, 338, 339 and 340, and around apulley 341 fixed upon the pivot 96 carrying the transverse referencecontact 94, so that when the piston 319 is moved in either direction thetransverse reference contact 94 of the gyroscopic stabilizer 50 will be.shifted accordingly to energize the corresponding solenoid 140 or 141and to swing the horizontal rudder 38 accordingly.

For yieldingly holding the shaft 300 in any position of rotativeadjustment, to selectively control the horizontal rudder, a disk 342 isrigidly mounted upon the shaft 300 and' is provided with a plurality ofspaced peripheral V-shaped notches 343, 344, 345, 346 ada ted to receivea V-shaped catch 347 which is fixed u on one end of a spring 348, theother end 0 which is secured to a fixed support 349, the catch 347 beingnormally pressed against the disk 342 by the spring 348 and beingarranged to hold the shaft 300 and consequently the transverse referencecontact 94 in any position of adjustment durin the automatic operationof the aeroplane, fiut to yieldingly permit the adjustment of thetransverse reference contact 94 through the action of the piston 319under suitable pneumatic pressure during the selective control of thehorizontal rudder of the aeroplane by an operator from a distantstation.

For selectively controlling the ailerons 40, 41 by changing the positionof the longitudinal reference contact 102, a power cyl1nder 350 is fixedupon the aeroplane 'and is provided with a reciprocatory piston 351 xedupon a piston rod 352 extending slidably through the power cylinder andalso through a centering device including a. fixed spring cylinder 353,provided to center the iston 351 in its cylinder 350, this center.- 1ngdevice being similar in construction to that hereinbefore describedincluding the spring cylinder 320 for controlling the horizontal rudder.The outer end of the piston rod 352 is connected to an endless rope orwire 355 which passes around idlers 356, 357, 358. and 359 and around apulley 360 rigidly secured to the pivot 104 upon which the longitudinalreference contact 102 is mounted. The opposite ends of the cylinder 350are connected respectively by pipes 365 and 367 with the transversepassages 292 and .293 through the casing of the rotary valve 200. Needlevalves. 368 and 369 are placed in the pipes 365 and 367 and areadustable to retard or to relatively facilitate the flow of air throughthe pipes to time the the rotary valve 200 and the other end of relativemovement of the ailerons 40, 41 with respect to the selective movementof the vertical rudder 35 as will appear herein' after. By thisconstruction compressed air may be admitted from the source of supply199 selectively to either end of the cylinder 350 and exhausted from theother end to move the piston 351 to shift the longitudinal referencecontact 102 accordingly to energize the corresponding solenoid .142 or143 and to swing the-ailerons 40, 41 accordingly.

For selectively controlling the vertical rudder 35 a power cylinder 375is provided,

one end of which is connected by a pipe 376 to the passage 273 in thecasing201 of spring centering means is provided substantially the samein construction and operation as that hereinbefore described andincluding a fixed cylinder384 a reciprocatory rod 385 extending throughthecylinder, a spiral spring 386 and two discs 387, 388 looselysurrounding the rod, and two collars 389, 390 fixed upon the rod andarranged to reciprocate through the opposite ends of the cylinder 384respectively. The outer end of therod 385 carries a pin 391 whichengages slidably in a slot 392 in the lever 382.

Rigidly secured to and projecting transversely from the lever 382 is abar 395 the outer end of which is secured by rope or wire 396 whichextends over idlers 397, and the ends of which are connected to the endsof a rod 399 perpendicular to and rigid with the vertical rudder 35.Needle valves 398 and 399 are laced in thepipes 376 and 377 and areadjustable to retard or to relatively facihtate the flow of air throughthe pipes to time the selective movement of the vertical rudder 35 withrespect to the selective movement of the ailerons 40, 41. By thisconstruction when the iston is moved in either direction the verticalrudder 35 will be oscillated accordin l dr selectively connecting anddisconnecting the arm 175 to the azimuth gyroscope 55, to permit of thecontrol of.the vertical rudder 35 either automatically or selectively asmay be desired, the arm, 175- is fixed upon the upper end of a stem 400which extends vertically downwardly from the arm and which is arrangedto rotate snugly in and with respect to a sleeve 401, to which thespaced contacts 176 and 177 and the outer ends of the springs 178 and179 are rigidly secured, and which is connected tothe gyroscope and ismaintained thereby in a vertical position and is held thereby againstrotation in space about a vertical axis. The lower end of the stem isrigid with the upper end of a hollow cylinder 402 in which is a piston403 which is rigid with the upper end of a piston rod 404 which projectsdownwardly through the lower end of the cylinder and through the upperend of a hollow head 405 which is rigid with the upper end of a rod orstem 406 which is a part of the gyroscope and which is always maintainedthereby in a vertical position and is always held thereby againstrotation in space with respect to its vertical axis. Rigid with thepiston rod 404 and within the head 405 is a clutching disk 407 andwithin the cylinder 402 and surrounding the' piston rod 404 is a spiralspring which normally forces the piston upwardly and causes the disk 407to clamp the cylinder 402 and head 405 rigidly together. An axialpassage 408 leads upwardly from the cylinder through the stem 400 andcommunicates at its upper end with an annular recess 409 in the-stemwhich always communicates through a pipe 410 with the transverse passage271 through the casing of the rotary valve 200 whereby by suitablypositioning the rotary valve 200 compressed air may be admitted to thecylinder 402 to release the arm 175 from the control of the gyroscope 55or may be exhausted from the cylinder 402 to permit the arm 17 5 to becontrolled by the gyroscope 55.

For automatically controlling the vertical rudder 35 of the aeroplane asa result "of the co-operative action between the arm 175 of the azimuthgyroscope 55 and the spaced contacts 176 and 177, an electromagneticvalve is interposed between the source" of airsupply 199 and the rotaryvalve 200. The electro-magnetic valve includes a cylindrical casing 424in which is arranged to reciprocate a piston valve 425 which is providedwith three annular recesses 426, 427, 428, the central one of which 426normally communicates with the source of air 'supply through an inletport 429 and pipe 430. The outer annular recesses 427, 428, normallycommunicate respectively with exhaust ports 430, 431 and through twooutlet ports 432, 433, and pipes 434 and 435 withthe passages 282, 281through the casing of the rotary valve 200. The piston valve is normallyyieldingly centered in its casing by two opposed spiral springs 434',435'.

For reciprocating the piston valve 425 to ,control the vertical rudder35, the valve is vertical rudder may The outer ends of these solenoidsare connected by electric conductors 440, 441 with the two fixedcontacts 176 and 177 respectively, and the inner end of these twosolenoids are connected by conductors 442 and 443 to a common returnconductor 444 which is arranged as will appear hereinafter to benormally connected through suitable helm limiting means and a battery448'to the arm 175 of the azimuth gyroscope 55. I

In controlling the vertical rudder of the aeroplane automatically, ifthe azimuth gyroscope 55 were permitted to function freely, the verticalrudder would be oscillated through a wide angle approximately through anangle of thus steering the aeroplane laterally first in one directionand then in an opposite direction on an appreciably zigzag course. Toavoid such a zigzag movement, and to hold the aeroplane 1n anapproximately straight or true course, the common return conductor 444is connected to a movable contact 445 fixed upon but insulated from thepiston rod 379 which nected by a conductor 447 with one pole of abattery 448 the other pole of which is connected by a conductor 449 withthe arm 175 of the azimuth gyroscope 55. In this construction the anglethrough which the be moved automatically may be varied by c anging thelength of the elongated contact 446 either by substitution or otherwise.

r In the operation of this improved aeroplane when it is desired to havethe stabilizing and steering performed entirely automatically by thegyroscopes, the rotary valve is adjusted into the position shown :1I1Fig. 10 which may be called the first position, or in a position whichmay be called the fourth osition, (not shown) which is reached yrotating the valve through 180 degrees from its first position. When thevalve is in either of these positions, the pressure cylinder 402 of theclutch of the azimuth gyroscope is permitted to exhaust through pipe 410and recesses 265 or 267 and 250 of the rotary valve and exhaust outlet255 thus permitting the spiral spring to connect the arm 175 rigidly tothe stem 406 of the gyroscope to permit the gyroscope 55 to function intheautomatic control of the vertical rudder 35.

'Also when the aeroplane is being automatically controlled and therotary valve 200 is in either its first or its fourth position, theopposite ends of the cylinder 375 for selectively controlling thevertical rudder are normally open to exhaust through the pipes 376, 377,passages of the rotary valve 277 and 279, pipes 434 and 435 and exhaustports 430 and 431 of the solenoid valve respectively, thus permittingthe spring actuexhaust through the pipes 365 and 367, re

cesses 287 and 290 or 290 and 287 of the rotar permit the springcentering means 353 to center the longitudinal reference contact 102 ofthe gyroscopic stabilizer 50 for automatically controlling the ailerons40, 41.

Also, when the rotary valve 200 is either in its first or fourthposition, the opposite ends of the cylinder 318 for selectivelycontrolling the horizontal rudder 38 are normally open to exhaustthrough the pipes 330 and 331, longitudinal recesses 278 and 280, of therotary valve 200 and transverse passages or exhaust ports 283 and 284respectively to permit the spring centering means contained in thecylinder 320 to center the piston 319 and the rack 316 which is donewithout disturbing the position of the transverse reference contact 94of the gyroscopic stabilizer 50 for automatically controlling thehorizontal rudder 38.

In automatically controlling the aeroplane with respect to a verticalaxis, if, on account of ci'oss currents in the air or for Valve and theexhaust port 259 to any other reason the aeroplane should be slightlyrotated in either direction about a vertical axis, or in other wordsslightl y diverted laterally from a given course, and to such an extentthat the aeroplane rotates with respect to the arm 175 until the freeend of the arm comes into engagement with 'one orthe other of thecontacts 176, 177 vfixed upon the aeroplane, then the correspondingsolenoid 438 or 439 would be energized and draw the solenoid valve 425towardsit and place the corresponding end of the cylinder 375, forcontrolling the vertical rudder, into communication with the source 199of air supply through the corresponding pipes 434 the len th of theelongated contact 446.

When t e vertical rudder has been moved.

wards a central position by the spring actu ated rod 385 until themovable contact 445 is returned into engagement with the elongatedcontact 446, whereupon if the arm 17 5 is still in engagement with oneof the spaced contacts 176, 177 thecurrent will be restored through thecorresponding solenoid 438 or 439 and the vertical rudder will be againmoved accordingly as hereinbefore described to restore the aeroplaneapproximately to the given'course. This breaking and remaking of thecurrent by the movement of the contact 445 out of and into engagementwith either end of the elongated contact-446 will be automaticallyrepeated, if necessary, to cause a slight reciprocatory or fluctuatingmovement of the piston 378 upon the corresponding side of its centralposition and a correspondingly slight fluctuating or oscillatingmovement of the vertical rudder 35 upon the corresponding side of itscentral position until the aeroplane has been restored approximately tothe given course. But when the vertical rudder is being controlledselectively the azimuth gyrosco e is rendered temporarily ineffective anthe Vertical rudder is permitted to be moved through a comparativelywide angle as will appear hereinafter.

In automatically controlling the aeroplane with respect to a transversehorizontal axis to keep the aeroplane moving either .in a predeterminedhorizontal plane or in a predetermined inclined plane either upwardly ordownwardly, the transverse reference contact 94 is firstcorrespondinglyv adjusted by rotatively adjusting the shaft 300 so thatthe catch 347 will engage inv a suitable notch. For instance the notches343, 344, 345 etc. are so arranged that when the catch is arranged asshown in Fig. 7 in a particular notch 344 the transverse referencecontact 94 will be in a central position so that when the aeroplane isproceeding in a horizontal course, the transverse reference contact 94will rest upon the intermediate insulation 93 and any deviation of theaeroplane from a horizontal course will cause the corresponding one ofthe segmental contacts 91 and 92 to engage the transverse referencecontact 94 and energize the corresponding solenoid 140 or 141 tooscillate the horizontal rudder accordingly to restore the aeroplane toa horizontal course. In a similar manner the transverse referencecontact 94 may be adjusted either in one directioin or the other from acentral position, so as to co-operate with the segmental contacts 91 and92 in maintaining the aeroplane automatically either in an upwardly or adownwardly inclined course.

In the automatic control of the aeroplane with respect to itslongitudinal axis, as a result of the co-operation between thelongitudinal reference contact 102 and corresponding segmental contacts99 and 100, the longitudinal axes of the two transverse main planes 30,31 are normally maintained in substantially horizontal positions, or inother words the aeroplane is normall ke t from rotating about itslongitudina axis. When the aeroplane tilts slightly from itsnormalposit'ion in either direction about its longitudinal axis, thecorres onding segmental contact 99 or 100 will be rought into engagementwith the longitudinal reference contact, which normall rests upon theinsulation 101 between t e two segmental contacts, and the correspondingsolenoid 142 or 143 will be energized to oscillate the two ailerons 40,41 simultaneously in opposite directions accordingly'to restore theaeroplane to a normal position with respect to its longitudinal axis.

In selectively controlling the aeroplane laterally or with respect to avertical axis, when it is desired to turn the aeroplane laterallytowards the right from a given path, the rotary valve 200 is advanced,in response to suitable impulses of radiant energy (shown in' Fig. 10)into a position shown in Fig. 11 which may be called the second positionof the valve which is 60 degrees in advance of its first position,-

shown inFig. 10. When the valve is in its second position, air isadmitted from the source of supply v199 through pipes 202, branch pipe203 passage 25 8 recess 286, passage 292 and pipe 365 to the left handend (viewing Fig. 2) of the cylinder 350 and the right hand end of thecylinder 350 is open to exhaust through the pipe 367 passage 293 recess289 and exhaust assage or port 259. The' piston rod 352 ist us forced tothe right and by means of wire 355 rotates the longitudinal referencecontact 102 into engagement with the segmental contact 100 andconsequently energizes the solenoid 143 which swings the free end of theaileron 40 upon the right side of the aeroplane upwardly andcorrespondingly depresses the free end of the ailerofii41 upon the leftside of the aeroplane,'eonse-, quently rotating or tilting theaeroplaneabout its longitudinal axis by lowering the ri ht side of theaeroplane and raising its legt side thus suitably banking the aeroplaneto facilitate a lateral turning of'the aero lane to the right about avertical axis. At the same time that the aeroplane is being banked asjust described, for turning laterally towards the right, compressed airis admitted from the source 199 through the pipe 202 passage 256 recess272 pipe 376 to the right hand end of the cylinder 375, and the lefthand end of the cylinder 375 is open to exhaust through the pipe 377passages 275, 285 and exhaust port or passage 257. The piston 378 isthus forced towards the left, and by means of wire 396 swings the freeend of the vertical rudder 35 towards the right to turn the aeroplanelaterally towards the right.

By a process the reverse of theone just described when the rotary valvehas been rotated into its fifth position (not shown), 180 degreesfrom-the second position shown in Fig. 11, in response to suitableimpulses of radiant energ the free end of the left hand aileron 41 1ssimultaneously raised to bank the aeroplane for turning towards the leftand the free end of the vertical rudder is turned towards the left toturn the aero lane laterally towards the left.

W en the aero lane is being selectively steered laterally t rough theaction of the vertical rudder 35 and the ailerons 40, 41 as justdescribed, the automatic control of the vertical rudder by the azimuthgyroscope is temporarily discontinued autopassage 274 and ipe 330 to theright hand end of the cylin er 318; and the left hand end of thecylinder 318 is open to exhaust towards the left moving the ratchetmechanmatically by the admission of compressed air from the source 199through the pipe 202, annular recess 251 longitudinal recess 270 or 269,passage 271 and pipe 410 to the gyroscope which disconnects the arm 175from the gyroscope as hereinbefore described.

Also, when the aeroplane is being selec-' tively steered laterally, bothends of the cylinder 318' are automatically opened to exhaust throughthe pipes 330 and 331 longitudinal recesses 277 and 279 and exhaustports 283 and 284 respectively, thus permitting the horizontal rudder 38to be controlled automatically by the gyroscopic pressed air is admittedfrom the source 199.

through the pipe 202 passage 256 annular rec$ 25 l g tudinal recess 27 2transverse ismor shaft 300 and the wire 336 accordingly and shifting thetransverse reference contact 94 rearwardly, and the free end of the.horizontal rudder 38 is pulled downwardly 'thus turning the aeroplanedownwardly as hereinbefore described.

When it is desired to rotate the aeroplane about a horizontal axis so asto direct the aeroplane upwardly from a given path and in apredetermined plane, the rotary valve 200 is rotated into its sixthposition (not shown), 180 degrees in advance of its third position,shown in Fig. 12, and by a process the reverse of the one just describedwhen the valve is in this position the free end of the horizontal rudder38 will be moved upwardly to turn the aeroplane upwardly.

When the aero lane is being selectively steered vertically y the actionof the hori zontal rudder 38 as just described, the pneumatic clutch ofthe azimuth gyroscope 55 is in communication with the exhaust port 255through the pipe 410. longitudinal recess 268 or 266 and annular recess250 .to permit the azimuth gyroscope to control the vertical rudder 35automatically as hereinbefore described.

Also, when the aeroplane is being seleccglinder 350 are open to exhaustthrough t e pipes 365 and 367, longitudinal recesses 291 and 288 or 288and 291, annular recess 254 and exhaust port 259, to ermit of thecentralization of the longitudlnal reference tively steered verticallyboth ends of the contact 102 and the automatic stabilizing of theaeroplane about its longitudinal axis by the roscopic stabilizer 50acting through t e ailerons 40 and 41 as hereinbefore described.

It is also to benoted that in the selective control of the aeroplanevertically or about a transverse horizontal axis through the action ofthe horizontal rudder 38, and inthe selective control of theaeroplaneabout.

its longitudinal. axis through the action of the ailerons 40, 41, thehorizontal rudder.

and the ailerons are separately controlled through the action of thegyrosco ic stabilizer 50 to rotate the aeroplane t rough a predeterminedangle about and into .a predetermined position with respect to thetransverse horizontal axis, and to rotate the aeroplane through apredetermined angle about, and into a predetermined position withrespect to its longitudinal axis, and to stabilize the aeroplane in eachof those positions, the angle of rotationand the resultant stabilizedposition in each case being predetermined by selectivel positioning thetransverse and longitu inal reference contacts 94 and 102' respectivelyas hereinbefore described.

In steering the aeroplane selectively the rotary valve 200 may berotated so quickly from any given position through one or moreintermediate positions to a second given position that noappreciableefi'ect is produced upon the control or movement of theaeroplane as the valve passes through the intermediate position orositions. It is therefore possible to selectively control 'the movementof the aeroplane laterally and about its longitudinal axis, orvertically as hereinbefore described.

Although only a single form has been described in which this inventionmay be embodied, it is to be understood that the invention is notlimited to any specific construction but may be ap lied in various formsto be controlled either by electromagnetic. or Hertzian waves ashereinbefore described or by light waves, sound waves, or any other formof energy without departing from the spirit of the invention or thescope of the appended claims.

Having thus fully described this invention, I claim and desire toprotect by Letters Patent of the United States;

1. The combination with a dirigible body of means carried thereby andmovable with respect thereto for rotating said body about an axisextending longitudinally thereof, means cooperating with said firstmentioned means for automatically stabilizing said body with respect tosaid axis, and means responsive to radiant energy and acting throughsaid stabilizing means for rotating said body selectively about saidaxis through the actionof tioned means.

2. The combination with a dirigible body, of means carried thereby andmovable with respect thereto for rotating said body about a plurality ofaxes, means carried by said body and coo erating with said firstmentionedflneans or stabilizing said body with respect to each of saidaxes and means responsive" to radiant energy and acting through saidstabilizing means for rotating said body selectively with respect to oneof said axes and then with respect to another of said axes, orsimultaneously with respect to a plurality of said axes, in response toradiant energy from a fixed source.

3. The combination with a dirigible body provided with means movablewith respect thereto for tilting or rotating said body about itslongitudinal axis or line of movement of stabilizing means arranged tocooperate automatically with said first mentioned means to oppose anytilting or rosaid first menrom a distance tation of said body about saidaxis and means responsive to radiant energy and acting through saidstabilizing means for modi ying the action of said stabilizing meansupon said first mentioned means.

4. The combination with a dirigible body provided with means forbanking, tilt ing or rotating said body in either direction about itslongitudinal axis or line of motion, and for turning said body laterallyeither in one direction or in an opposite direction, of stabilizingmeans, carried by said body and arranged to cooperate automatically withsaid first mentioned means to oppose any such tilting or turning of saidbody, and means responsive to radiant energy for modifying the action ofsaid stabilizing means upon said first mentioned means, 5. Thecombination with a dirigible body of means carried thereby and movablewith respect thereto for causing said body to deviate vertically from agiven course, means carried by said body and movable with rcspectthereto for causing said body to deviate laterally from a given course,stabilizing means automatically cooperating with said first mentionedmeans and with said second mentioned means for opposing any deviation ofsaid body either vertically or laterally from a given course, and meansresponsive to radiant energy for selectively modify-- ing the normaloperation of said stabilizin; means and causing said body to deviaiceither vertically or laterally from a given course in response toradiant energyfrom a fixed source.

' 6. The combination with a dirigible body of means carried thereby tocause said body to deviate from a given course, stabilizing meansautomatically operative to oppose any appreciable deviation of said bodyfrom said given course and means responsive to radiant energy andoperative to overcome the normal effect of said stabilizing means and tocause said body to deviate vertically through any desired are from saidgiven course in response to radiant energy from a fixed source.

7. The combination with a-dirigible body of means carried thereby tocause said body to deviate from a given course, stabilizing meansautomatically operative to oppose any appreciable deviation of said bodyeither vertically or laterally from said given course and meansresponsive to radiant energy and operative in response to radiant energyfrom a fixed source to overcome the normal effect of said stabilizingmeans and to cause said body to deviate selectively either laterally orvertically through any desired arc in either direction from said course.

8. The combination with a dirigible body, of means carried thereby andmovable with respect thereto to cause said body to'deviate from a givencourse, stabilizing means auto III matically cooperating with said firstmen tioned means to maintain said body upon said course, and meansresponsive to radiant energy and operative to modify the normal effectof said stabilizing means and to cause said body to deviate eitherlaterally or vertically selectively from said course.

9. The combination with a dirigible body of means carried thereby andmovable with respect thereto to rotate said body about a longitudinalaxis, means 'carriedby said body and movable with respect thereto tocause said body to deviate laterally from a given course, stabilizingmeans normally cooperating with said first mentioned means to oppose anysubstantial rotation of said body about said axis, stabilizing meanscooperating with said'second mentioned means to move the sameindependently of said first mentioned means to oppose any substantiallateral deviation of said body from said course by said second mentionedmeans, and means responsive to radiant energy and operative to overcomethe normal effects of said firs t and second mentioned stabilizing meansand to simultaneously rotate said body about said longitudinal axis andto cause said body to deviate laterally from said course.

10. The combination with a dirigible body of means carried thereb andmovable with respect thereto for causing said body to rotate withrespect to a normally substantially horizontal axis, means forstabilizing said body in a given position of rotation with respect tosaid axis, and means responsive to radiant energy and operative inresponse to radiant energy from a fixed source to temporarilyovercomethe normal effect of said stabilizing means and to cause said body torotate from said given position through a predetermined angle and into asecond posi' tion of rotation with respect to said axis, saidstabilizing means being automatically operative to maintain said bodysubstantially in said. second position.

11. The combination with a dirigible body of means carried thereby andmovable with respect thereto for causing said body to rotate withrespect to an axis extending longitudinally of said body, meanscooperating .with said first mentioned means for-stabiliz} ing said bodyin a given position of rotation with respect to said axis, and meansresponsive to radiant energy and operative to temporarily overcome thenormal effect of said stabilizing means and to cause said body torotateirom said given position through a predetermined angle and into asecond position of rotation with respect to said axis, said stabilizingmeans being automatically operative to maintain said body substantial lyin said second position.

12. The combination with a dirigible body, of means, includingstabilizing means, carried thereby and normally effective to maintainsaid body automatically upon a predetermined course, and meansresponsive to radiant energy and operative in response to radiant energyfrom a fixed source to modify the normal effect ofsaid stabilizing meansand to selectively change the course of said body either vertically ineither direction or laterally in either direction.

13; The combination with a dirigible body of means carried thereby forsteering the same vertically in either direction, means carried by saidbody for steering the same laterally in either direction, means carriedby said body for banking or tilting the same to facilitate the turningof said body laterally, means normally automatically operative tostabilize said vertical steering means, said lateral steering means, andsaid banking or tilting means, and means actuated in re sponse toradiant ener y, either to ove rcome temporarily the e ect ofsaidstabilizing means upon said means for steering said body laterally andsaid means for banking said body and to bank or tilt said body and causesaid body to deviate laterally from said course or to overcometemporarily the normal effect of said stabilizing means u on said meansfor steering said body vertically and to cause said body to deviatevertically from said course. i

14. The combination with a dirigible body of means carried thereby andnormal-. 1y automatically operative to stabilize said body and to directsaid body upon a g ven course, and means responsive to radiant energyfrom a fixed source tomodify temporarily the operation of said stabilizng means and to cause said body to deviate either laterally orvertically from -said course and through any desired arc in eitherdirection.

15. A system for controlling an air craft ata distance by radiant energyincluding in combination, an aircraft body-having movable balancingmeans, a controller cooperating with said means and normally determiningthe balancing movement thereof automatically, and means responsive toradiant energy to modify the action of said controller upon saidbalancing means.

16.. A system for controlling an air craft at a distance by radiantenergy including in combination, an air craft body having movablebalancing means, a controller cooperating with said means and normallydetermining the balancing movement thereof automatically, and meansresponsiveto radiant energy from a'dis'tancc to modify the action, ofsaid controller upon said balancing means and to move said balancingmeans with respect to said body.

17. A system for controlling an. air craft by radiant energy, includingin combination an air craft body having balancing means, a controllercooperating with Said means and determining the position thereof, andmeans responsive to radiant-energy to modify the action of saidcontroller upon said balancing means. i

18. A system for controlling an air craft by radiant energy, includingin combination an air craft body having balancing means, a controllercoo crating with said means and determining t e position thereof, andmeans responsive to radiant energy to vary the action of said controllerupon said balancing means.

19. The combination with a movable body, of means to stabilize said bodywith respect to an axis extending substantially longitudinally thereof,and means operative in response to radiant energy to modify the actionof said stabilizing means and to rotate said body about an axisextending transversely thereof.

20. The combination with a movable body, of means to stabilize said bodywith respect to an axis extending substantially longitudinally thereof,and means operative in response to radiant energy to vary thestabilizing actionof said stabilizing means and to rotatesaid body aboutan axis extending transversely thereof and normally substantially"ertically.

21. The combination with -a movable body, of means to stabilize saidbody with respect to an axis extending substantially longitudinallythereof, and means. operative in response to radiant energy to modifythe action of said stabilizing means and to rotate said body about anaxis extending transversely thereof and normally substantiallyvertically.

22. The combination with a movable body, of means to stabilize said bodywith respect to an axis extending substantially longitudinally thereof,and means operative in response to radiant energy to vary the action ofsaid stabilizing means 'and to rotate said body about an axis extendingtransversely thereof.

23. The combination with a movable body, of means including an elementcarried by said body and arranged to swing in response thereto tostabilize said body with respect to an axis extending substantiallylongitudinally thereof, and means operative in response to radiantenergy to modify the action of said stabilizing means and to rotate saidbody about an axis extending transversely thereof. 7

24. The combination with a movable body, of means including an elementcarried by said body and arranged to swing in response thereto tostabilize said body with respect to an axis extending substantiallylongitudinally thereof, and means operative in response to radiantenergy to modify the action of said stabilizing means and to rotate saidbody about an axis extending transversely thereof and normallysubstantially vertically.

25. The combination with a dirigible.

body, of means carried thereby for steering said body laterally ineither direction,

stabilizing means normally controlling said steerin means automatically,means carried by saif body for tilting said body in either directionabout an axis extending longitu- I neously steer said body laterally ineither direction selectively and tilt said. body about.

its longitudinal axis either in one direction or in an oppositedirection depending upon the direction in which said body is beingdiverted laterally.

26. The combination with a dirigible bod of means carried thereby forsteering said body laterally in either direction, stabilizing meansnormally controlling said steering means automatically, means carried bysaid body for tilting said bod in either direction about an axisextending longitudinally thereof, gyroscopic stabilizing means normallcontrolling said tilting means automatical y, and means operative inresponse to radiant energy to modify the action of said first-mentionedstabilizing means and said second-mentioned stabilizing means and tosimultaneously steer said body laterally in 'either direction se-flectively and tilt said body about its longitudinal axis either in onedirection or in an opposite direction de ending upon the directlon inwhich said body is being diverted laterally.

27. In combination, an aircraft, means called into action upon change inheading of said aircraft for restoring it to a predetermined heading andmeans controllable from a distance for' cha 'ng saidpredeterminedheading to any isired heading.

28. In-combination, an aircraft, a gyroscopic pendulum mounted thereon,a controlling plane controlled by said pendulum and means controllableby radiant energy for changing the elfective relationship between saidpendulum and plane.

29. In combination, a self-stabilizing, self-steering aircraft, andmeans comprising a radiant energy transmission system for causing saidaircraft to make an deglireld turn in azimuth at any point in its 30. Incombination, a self-stabilizing, self-steering aircraft, meanscomprising a radiant energy transmission system for causing saidaircraft to make any desired turn in azimuth at any point in its flight,

and means for automatically banking the craft while turning. 1

31. The combination with a dirigible body of means carried thereby andmovable with respect thereto for causing said body to deviate verticallyfrom a given course, means carried by said body and movable with respectthereto for causing said body to deviate laterally from a given course,stabilizing means automatically cooperating with said first mentionedmeans and with said second mentioned means for opposing any deviation ofsaid body either vertically or laterally from a given course, and meansresponsive to radiant energy for selectively modifying the normaloperation of said stabilizing means and causing said body to deviateeither vertically or laterally from a given course, in response toradiant energy;

32. The combination with a dirigible body, of means carried thereby tocause said body to deviate from a given course, stabilizing meansautomatically operative to oppose any appreciable deviation of said bodyfrom said given course and means responsive to radiant energy andoperative to overcome the normal effect of said stabilizing means tocause said body to deviate vertically through any desired are from saidgiven course in response to radiant energy.

In testimony whereof I hereunto aflix my signature.

JOHN HAYS HAMMOND, JR.

